| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
"さきがけ(1985-001-A)" および "すいせい(1985-073-A)" の姿勢・軌道制御系の設計 |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
|
資源タイプ |
departmental bulletin paper |
| その他のタイトル（英） |
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その他のタイトル |
Design of the Attitude and Orbit Control System of "SAKIGAKE (1985-001-A)" and "SUISEI (1985-073-A)" |
| 著者 |
二宮, 敬虔
上杉, 邦憲
村中, 昇
加藤, 昭夫
北出, 賢二
滑, 孝和
卯尾, 匡史
NINOMIYA, Keiken
UESUGI, Kuninori
MURANAKA, Noboru
KATOH, Akio
KITADE, Kenji
NAMERA, Takakazu
UO, Masashi
|
| 著者所属 |
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日本電気(株)宇宙開発事業部制御システム開発部 |
| 著者所属 |
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日本電気(株)宇宙開発事業部制御システム開発部 |
| 著者所属 |
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日本電気(株)宇宙開発事業部制御システム開発部 |
| 著者所属 |
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日本電気(株)宇宙開発事業部制御システム開発部 |
| 著者所属 |
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日本電気(株)宇宙開発事業部制御システム開発部 |
| 出版者 |
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出版者 |
宇宙科学研究所 |
| 書誌情報 |
宇宙科学研究所報告
巻 37,
p. 1-62,
発行日 1986-06
|
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
"SAKIGAKE", Japan's first interplanetary spacecraft was successfully launched on January 8,1985.Its mission was to verify the launch capability of the then newly developed Mu-3SIIvehicle and the technology applied to "SUISEI", Japan's Halley's comet explorer launched later the same year on August 19. These spacecraft are spin-stabilized at about 6rpm spin rate, and have same configuration except, of course, for the differing scientific payloads. To assure the communication link between the spacecraft and the ground station, a high-gain parabolic antenna mechanically despun with respect to the spinning spacecraft, is used. In order to provide SUISEI with the ability for ultraviolet imagery of the comet, while satisfying, thermal constraints of the onboard instruments, the spacecraft were also designed so that their spin-rate could be reduced to a low and stable value of around 0.2rpm by spinning up a momentum wheel. The imagery instrument uses the time-delay-and-integration scheme of a 2-dimensional charge coupled device sensor to obtain unblurred pictures of the comet at this spacecraft spin rate. For attitude and orbit control actuator, a hydrazine (N_2H_4) monopropellant propulsion system was developed. Attitude sensors consist of a spin-type sun sensor and a star scanner. Thus far, the attitude and orbit cotrol systems have functioned properly so these spacecraft should be able to fully complete their mission goals. In this report, the function and the detailed design of the attitude and orbit control system of SAKIGAKE and SUISEI are described, together with the analyses pertinent to the design and the operation. The flight results to verify the design are also presented. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0285-2853 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AN00354474 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0166130000 |
SA0166130.pdf (2.9 MB)
